CN102085919A - Collision triggered non-cooperative target docking capture mechanism - Google Patents
Collision triggered non-cooperative target docking capture mechanism Download PDFInfo
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- CN102085919A CN102085919A CN2011100208415A CN201110020841A CN102085919A CN 102085919 A CN102085919 A CN 102085919A CN 2011100208415 A CN2011100208415 A CN 2011100208415A CN 201110020841 A CN201110020841 A CN 201110020841A CN 102085919 A CN102085919 A CN 102085919A
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Abstract
一种航天技术领域的碰撞触发式非合作目标对接捕获机构，包括：碰撞杆、连杆、卡塞、粘接体、弹簧、对接体外壳和限位挡环，碰撞杆位于刚性对接机构的中心轴上，两组连杆收尾相连且中心与两端分别与碰撞杆和卡塞相连接，两组卡塞分别与对应的两个粘接体以及对接体外壳固定连接，弹簧的两端分别与粘接体的底部和对接体外壳的底部相连接，限位挡环位于对接体外壳的顶端。本发明在吸收传统对接机构优点的基础上，设计自主依靠碰撞触发的机械刚性对接机构，实现对目标航天器无外形和运行状态限制的要求，具有结构简单、成本低、可靠性高等性能。
A collision-triggered non-cooperative target docking capture mechanism in the field of aerospace technology, comprising: a collision rod, a connecting rod, a jam, a bonding body, a spring, a docking body shell and a limit stop ring, and the collision rod is located at the center of the rigid docking mechanism On the shaft, the two sets of connecting rods are connected at the end and the center and both ends are respectively connected with the collision bar and the jamming plug. The bottom of the bonding body is connected with the bottom of the docking body shell, and the limit stop ring is located at the top of the docking body shell. On the basis of absorbing the advantages of the traditional docking mechanism, the present invention designs a mechanically rigid docking mechanism independently triggered by collision, and realizes the requirement of no restriction on the shape and operating state of the target spacecraft, and has the properties of simple structure, low cost, and high reliability.
Description
Technical field
What the present invention relates to is the device in a kind of space technology field, specifically is a kind of collision trigger-type noncooperative target butt joint capture mechanism.
Background technology
Autonomous butt joint capture technique towards noncooperative target can carry out catching and operating at rail to any fault spacecraft, effectively prolongs the life-span of fault spacecraft, also can be used for hostile passive space vehicle is hit and destroys, and has very big military value.Autonomous butt joint capture mechanism is a critical component of realizing noncooperative target butt joint capture technique.At present the docking mechanism that adopts at noncooperative target in the world mainly contains with the satellite engine nozzle and is the docking mechanism of mating interface and flies the flexible capture mechanism that net is the means of catching with flexibility.
Find through literature search prior art, people such as Liang Bin, Zhai Guang is at robot, in September, 2008, the 30th the 5th phase of volume, delivered " in rail capture technique development Overview " literary composition on the 467-480 page or leaf, this article has proposed a kind ofly to fly the flexible acquisition mode that net is the means of catching with flexibility, flexibility flies net and adopts the free flight platform and fly net and launch the mode that acquisition equipment combines at the rail capture systems, fly net and catch in the active distance of operation when target enters flexibility, fly net and directed target is launched, opened and envelope locking target.Its weak point is to adapt to Large Spacecraft to the catching of small-sized spacecraft, orbit maneuver cost height, and passive space vehicle can't be resumed work after being hunted down again.
Summary of the invention
The present invention is directed to the prior art above shortcomings, a kind of collision trigger-type noncooperative target butt joint capture mechanism is provided, on the basis that absorbs traditional docking mechanism advantage, the autonomous mechanical rigid docking mechanism that relies on collision to trigger of design, realization does not have the requirement of profile and running state restriction to passive space vehicle, has simple in structure, performances such as cost is low, reliability height.
The present invention is achieved by the following technical solutions, the present invention includes: collision bar, connecting rod, jam, convered structure, spring, butt joint body shell and limit baffle ring, wherein: collision bar is positioned on the center shaft of rigidity docking mechanism, two groups of connecting rods ending links to each other and the center is connected with jam with collision bar respectively with two ends, two groups of jams are captiveed joint with cooresponding two convered structures and butt joint body shell respectively, the two ends of spring are connected with the bottom of convered structure and the bottom of butt joint body shell respectively, and limit baffle ring is positioned at the top of butt joint body shell.
Described collision bar is the cylinder body rod.
Described two groups of connecting rods are the transmission that 180 ° of circumference are symmetrically distributed and realize tampering action power.
Described two groups of jams are 180 ° of circumference and are symmetrically distributed.
Described convered structure is the cylinder ring body, and the inwall of this convered structure and mechanism shell body closely cooperates and is distributed in mechanism's first half, and the bonding plane of convered structure is provided with the adhesive bond material with bonding target star.
Described spring is a holddown spring, and this spring imposes outside elastic force to convered structure.
Described limit baffle ring is captiveed joint with mechanism shell.
Satellite is caught in utilization of the present invention and the impact force between the target star of being hunted down triggers and to finish docking operation: catch satellite and approach the target star that is hunted down along default certain track, catching satellite control system sends instruction and will dock capture mechanism and eject from celestial body, docking mechanism is close to the flight of target star with certain initial velocity, collision bar at first contacts with the target star, rely on the effect of this impact force, connecting rod rotates, fixedly jam is pulled out in drive, convered structure flies out under the elastic force effect of bottom preloading spring, finally stop, clinging the target star in the limit baffle ring position.
Compared with prior art, docking mechanism of the present invention adopts the weak collision docking mode with catching satellite body, does not have complicated ACTIVE CONTROL system, and cost is relatively low; Mechanism is simple and reliable, and acquisition procedure is fully autonomous; Sphere of action is big, and the target star that adapts to the different maneuvering conditions of different task is caught demand; The target star is not had specific (special) requirements, do not limit the satellite structure characteristics that are hunted down.
Description of drawings
Fig. 1 is a structural representation of the present invention.
The specific embodiment
Below embodiments of the invention are elaborated, present embodiment is being to implement under the prerequisite with the technical solution of the present invention, provided detailed embodiment and concrete operating process, but protection scope of the present invention is not limited to following embodiment.
As shown in Figure 1, present embodiment comprises: collision bar 1, connecting rod 2, jam 3, convered structure 4, spring 5, limit baffle ring 6 and docking mechanism shell 7, wherein: collision bar 1 is positioned on the center shaft of docking mechanism, two groups of connecting rods, 2 endings link to each other and the center is connected with jam 3 with collision bar 1 respectively with two ends, jam 3 is captiveed joint convered structure 4 with docking mechanism shell 7, the two ends of spring 5 are connected with the bottom of convered structure 4 and the inside face of docking mechanism shell 7 bottoms respectively, and limit baffle ring 6 is positioned at the top of docking mechanism shell 7.
Described collision bar 1 is the cylinder body rod, begins the structure that bumps with the target star most, and effect is to provide propulsion source for whole docking operation.
Described connecting rod is 180 ° of circumference for 2, two groups and is symmetrically distributed, and effect is to transmit tampering action power.
Described jam is 180 ° of circumference for 3, two groups and is symmetrically distributed, and offsets the spring force effect, and convered structure is fixed on the docking mechanism shell.
Described convered structure 4, its structure are that the inwall of cylinder ring body and mechanism shell body closely cooperates, and are distributed in mechanism's first half, and bonding plane is covered with the adhesive bond material, and effect is to eject bonding target star after collision takes place in docking mechanism.
Described spring 5 is in the pretension state always before the collision, effect provides the power that convered structure 4 outwards ejects.
Described limit baffle ring 6 is fixed together with mechanism shell 7, and effect is to keep collision bar 3 positions to be on the mechanism shaft line before the collision, and restriction convered structure 4 in collision back can not fly out outside the docking mechanism.
Described docking mechanism shell 7, its structure is a cylindrical cavity, supports whole docking mechanism.
During present embodiment work, catch satellite and approach the target star that is hunted down along default certain track, catching satellite control system sends instruction and will dock capture mechanism and eject from celestial body, docking mechanism is close to the satellite flight that is hunted down with certain initial velocity, collision bar 1 at first contacts with the target star, rely on the effect of this impact force, connecting rod 2 rotates, fixedly jam 3 is pulled out in drive, convered structure 4 flies out under the elastic force effect of bottom preloading spring 5, finally stop, clinging the target star in the position of limit baffle ring 6.
Be arranged on the big spacecraft than flying net formula docking mechanism, this device is applicable to that microsatellite implements to catch to the target star. The micro-nano satellite orbit maneuver can be realized the purpose that the time more economizes, fuel is more excellent, and bonding agency can serve as the part of target star structure with after the target star docks, and helps fault satellites to resume work.
Claims (7)
1. a collision trigger-type noncooperative target is docked capture mechanism, comprise: collision bar, connecting rod, jam, convered structure, spring, butt joint body shell and limit baffle ring, it is characterized in that: collision bar is positioned on the center shaft of rigidity docking mechanism, two groups of connecting rods ending links to each other and the center is connected with jam with collision bar respectively with two ends, two groups of jams are captiveed joint with cooresponding two convered structures and butt joint body shell respectively, the two ends of spring are connected with the bottom of convered structure and the bottom of butt joint body shell respectively, and limit baffle ring is positioned at the top of butt joint body shell.
2. collision trigger-type noncooperative target butt joint capture mechanism according to claim 1 is characterized in that described collision bar is the cylinder body rod.
3. collision trigger-type noncooperative target butt joint capture mechanism according to claim 1 is characterized in that described two groups of connecting rods are the transmission that 180 ° of circumference are symmetrically distributed and realize tampering action power.
4. collision trigger-type noncooperative target butt joint capture mechanism according to claim 1 is characterized in that described two groups of jams are 180 ° of circumference and are symmetrically distributed.
5. collision trigger-type noncooperative target butt joint capture mechanism according to claim 1, it is characterized in that, described convered structure is the cylinder ring body, the inwall of this convered structure and mechanism shell body closely cooperates and is distributed in mechanism's first half, and the bonding plane of convered structure is provided with the adhesive bond material with bonding target star.
6. collision trigger-type noncooperative target butt joint capture mechanism according to claim 1 is characterized in that described spring is a holddown spring, and this spring imposes outside elastic force to convered structure.
7. collision trigger-type noncooperative target butt joint capture mechanism according to claim 1 is characterized in that described limit baffle ring is captiveed joint with mechanism shell.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN2011100208415A CN102085919A (en) | 2011-01-19 | 2011-01-19 | Collision triggered non-cooperative target docking capture mechanism |
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| CN2011100208415A CN102085919A (en) | 2011-01-19 | 2011-01-19 | Collision triggered non-cooperative target docking capture mechanism |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102849228A (en) * | 2012-10-09 | 2013-01-02 | 黄刚 | Non-cooperative target docking mechanism with peripheral swing-rod-type expansion joint |
| CN103010490A (en) * | 2013-01-10 | 2013-04-03 | 中国人民解放军国防科学技术大学 | Docking rod |
| CN103303501A (en) * | 2013-05-17 | 2013-09-18 | 哈尔滨工业大学 | Adhesive aerosol absorbing and parasitizing mechanism and method for parasitizing adhesive dopa and derivatives aerosol on in-orbit aircraft through mechanism |
| CN104494846A (en) * | 2014-12-16 | 2015-04-08 | 中国空间技术研究院 | Universal weak-impact capture mechanism applicable to high-orbit satellites |
| CN104590590A (en) * | 2014-12-16 | 2015-05-06 | 中国空间技术研究院 | Multi-segment-type guiding and damping device applicable to space conical rod mechanism |
| CN105366077A (en) * | 2015-11-27 | 2016-03-02 | 中国空间技术研究院 | Locking release device applicable to satellite docking ring docking |
| CN105366078A (en) * | 2015-11-27 | 2016-03-02 | 中国空间技术研究院 | Holding type capture device applicable to satellite docking ring docking |
| CN105366079A (en) * | 2015-11-27 | 2016-03-02 | 中国空间技术研究院 | Compressing type locking device applicable to satellite docking ring docking |
| CN106114917A (en) * | 2016-07-05 | 2016-11-16 | 中国空间技术研究院 | A kind of damping unit with measurement function for the locking of satellites coupling ring |
| CN108502044A (en) * | 2018-03-21 | 2018-09-07 | 北京航空航天大学 | A Combined Separate Rotor and Foot Mobile Manipulation Robot |
| CN109911171A (en) * | 2019-04-30 | 2019-06-21 | 杜双昱 | Horn rotates synchronously structure and the industrial unmanned plane with the structure |
| CN112304547A (en) * | 2020-08-31 | 2021-02-02 | 中国空间技术研究院 | A free collision adsorption test device |
-
2011
- 2011-01-19 CN CN2011100208415A patent/CN102085919A/en active Pending
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102849228A (en) * | 2012-10-09 | 2013-01-02 | 黄刚 | Non-cooperative target docking mechanism with peripheral swing-rod-type expansion joint |
| CN103010490A (en) * | 2013-01-10 | 2013-04-03 | 中国人民解放军国防科学技术大学 | Docking rod |
| CN103303501A (en) * | 2013-05-17 | 2013-09-18 | 哈尔滨工业大学 | Adhesive aerosol absorbing and parasitizing mechanism and method for parasitizing adhesive dopa and derivatives aerosol on in-orbit aircraft through mechanism |
| CN103303501B (en) * | 2013-05-17 | 2015-05-06 | 哈尔滨工业大学 | Adhesive aerosol absorbing and parasitizing mechanism and method for parasitizing adhesive dopa and derivatives aerosol on in-orbit aircraft through mechanism |
| CN104494846A (en) * | 2014-12-16 | 2015-04-08 | 中国空间技术研究院 | Universal weak-impact capture mechanism applicable to high-orbit satellites |
| CN104590590A (en) * | 2014-12-16 | 2015-05-06 | 中国空间技术研究院 | Multi-segment-type guiding and damping device applicable to space conical rod mechanism |
| CN104590590B (en) * | 2014-12-16 | 2016-06-01 | 中国空间技术研究院 | A kind of multi-clove type guiding damping system being applicable to space Zhui Gan mechanism |
| CN105366079A (en) * | 2015-11-27 | 2016-03-02 | 中国空间技术研究院 | Compressing type locking device applicable to satellite docking ring docking |
| CN105366078A (en) * | 2015-11-27 | 2016-03-02 | 中国空间技术研究院 | Holding type capture device applicable to satellite docking ring docking |
| CN105366077A (en) * | 2015-11-27 | 2016-03-02 | 中国空间技术研究院 | Locking release device applicable to satellite docking ring docking |
| CN105366078B (en) * | 2015-11-27 | 2017-07-28 | 中国空间技术研究院 | A kind of tight-holding type acquisition equipment docked suitable for satellites coupling ring |
| CN105366079B (en) * | 2015-11-27 | 2017-08-29 | 中国空间技术研究院 | A kind of compression type locking device docked suitable for satellites coupling ring |
| CN106114917A (en) * | 2016-07-05 | 2016-11-16 | 中国空间技术研究院 | A kind of damping unit with measurement function for the locking of satellites coupling ring |
| CN108502044A (en) * | 2018-03-21 | 2018-09-07 | 北京航空航天大学 | A Combined Separate Rotor and Foot Mobile Manipulation Robot |
| CN108502044B (en) * | 2018-03-21 | 2020-10-13 | 北京航空航天大学 | Combined and separated rotor wing and foot type mobile operation robot |
| CN109911171A (en) * | 2019-04-30 | 2019-06-21 | 杜双昱 | Horn rotates synchronously structure and the industrial unmanned plane with the structure |
| CN109911171B (en) * | 2019-04-30 | 2023-11-14 | 杜双昱 | Synchronous rotating structure of horn and have industry unmanned aerial vehicle of this structure |
| CN112304547A (en) * | 2020-08-31 | 2021-02-02 | 中国空间技术研究院 | A free collision adsorption test device |
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Application publication date: 20110608 |